Exploring the Unknown: Selected Documents in ... - The Black Vault

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First Steps into Space: Projects Mercury and Gemini
3.2.3 In orbit, the capsule will have the configuration shown in figure 5(e) [not
included]. The retrograde maneuver shall be accomplished by firing
the spherical rocket motors mounted outside of the heat shield. These
motors shall then be jettisoned and the entry phase will be made by the
configuration illustrated in figure 5(f) [not included].
3.2.4 The capsule is to enter the atmosphere with the blunt face leading. The
aerodynamic heating at this face would be absorbed by the heat shield.
The area between this heat shield and the pressure vessel (in addition
to containing carry-through structure) would contain equipment which
is expendable at the time of deployment of the landing parachute, and
the heat shield along with this equipment shall be jettisoned at this time.
This operation will produce sizable reductions in the parachute loading
and will prevent conduction of heat from the hot shield into the pressure
vessel during the descent. The bottom contour of the pressure vessel shall
be designed from consideration of water and land impact loads. In addition,
an inflatable impact bag shall be used to absorb the shock of landing
(figure 5(h)) [not included].
[8]
3.2.5 In the event of a malfunction in the launch rocket system, on the ground
or in flight, the escape motors shall propel the capsule out of the danger
area in the configuration shown in figure 6(b) [not included]. This configuration
shall then coast in the pylon-first attitude until the dynamic
pressure approaches zero. At this point, the escape rocket system shall be
jettisoned and the capsule, with its new center of gravity, will be rotated
by aerodynamic moments (figs. 6(c) and 6(d)) [not included] until the
heat shield moves to the windward side. If the escape maneuver takes
place outside the atmosphere, the rotation of the capsule to the reentry
attitude shall be accomplished by means of an attitude control system of a
type to be specified in 4.2. At this point, the capsule configuration is [illegible]
illustrated in figure 5(f) [not included] for a normal flight. Parachute
deployment and heat shield separation shall then be as programmed for a
normal flight (fig. 5(g)) [not included].
[9]
4. STABILIZATION AND CONTROL
4.1 General - Stabilization and the control of the capsule shall be provided
in accordance with the following outline of the various phases of the
primary mission.
4.1.1 Launch- The launch trajectory control and guidance shall be considered an
integral part of the launching rocket system. This system (or systems) shall
make possible the missions described in Section 2 of this specification.
4.1.2 Orbit – After booster burn out and separation, the capsule shall be automatically
stabilized in attitude as specified in Section 4.2. An independent